航空发动机整机静子建模与刚度验证
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摘要
基于建立航空发动机整机状态的结构动力学分析有限元模型要求,对应用于静子机匣的不同有限元网格模型进行了对比分析,并将其组装成整机模型,进行了各支点的静柔度计算和对比试验。结果表明:对静子建模可分为主承力和其他机匣部件分别进行。承力机匣采用实体单元模型,有效模拟其刚度特性;传力机匣采用壳单元模型,在保证计算精度的前提下减小计算规模。通过对整机静子模型状态下轴承座静柔度计算与试验结果的对比,验证了整机静子模型刚度分布的有效性,经过质量修正后可以为整机状态结构动力学分析提供模型。
Different types of Finite Element Model(FEM) mesh model for the typical aeroengine stators were studied under the requirement of state FEM for structural dynamic of whole engine. A whole engine model was established by assembling the major engine stator, and the static flexibility of fulcrums were calculated and compared. The analysis result shows that the cases can be classified into two types. For the bearing support structures, the solid element should be used for appropriate idealization of the stiffness characteristics. For other engine cases, the shell element should be used to reduce computing scale on the premise of guarantee calculation precision. The stiffness characteristics was validated by comparing numerical result to the static flexibility test which was carried out during engine design process, and the model can be used in the whole engine structural dynamic analysis after the quality correction.
Different types of Finite Element Model(FEM) mesh model for the typical aeroengine stators were studied under the requirement of state FEM for structural dynamic of whole engine. A whole engine model was established by assembling the major engine stator, and the static flexibility of fulcrums were calculated and compared. The analysis result shows that the cases can be classified into two types. For the bearing support structures, the solid element should be used for appropriate idealization of the stiffness characteristics. For other engine cases, the shell element should be used to reduce computing scale on the premise of guarantee calculation precision. The stiffness characteristics was validated by comparing numerical result to the static flexibility test which was carried out during engine design process, and the model can be used in the whole engine structural dynamic analysis after the quality correction.
引文
[1]李文明.新机研制中整机振动及其限制值实践与思考[J].航空发动机,2002,(2):22-26.LI Wenming.Engine vibration and its limit in development of new engine practice and consideration[J].Aeroengine,2002,(2):22-26.(in Chinese)
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[8]晏砺堂,朱梓根.结构系统动力特性分析[M].北京:北京航空航天大学出版社,1987:25-26.YAN Litang,ZHU Zigen.Dynamics analysis of structures[M].Beijing:Beihang University Press,1987:25-26.(in Chinese)
[9]晏砺堂.航空燃气轮机振动和减振[M].北京:国防工业出版社,1991:30-31.YAN Litang.Vibration characteristics and decreasing method of aeroengine[M].Beijing:National Defense Industry Press,1991:30-31.(in Chinese)
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[12]陈果.航空发动机整机振动耦合动力学模型及其验证[J].航空动力学报,2012,27(2):241-254CHEN Guo.A coupling dynamic model for whole aeroengine vibration and its verification[J].Journal of Aerospace Power,2012,27(2):241-254(in Chinese)
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[14]周传月.SAMCEF有限元分析及应用实例[M].北京:机械工业出版社,2009:35.ZHOU Chuanyue.Finite element analysis and application example of SAMCEF[M].Beijing:China Machine Press,2009:35.(in Chinese)
[15]曾攀.有限元分析及应用[M].北京:清华大学出版社,2004:76.ZENG Pan.Finite element analysis and applications[M].Beijing:Tsinghua University Press,2004:76.(in Chinese)
[2]Moreno Barragan J A.Investigations into engine transient response due to internal and external dynamic excitations[R/OL].MTU Aero Engines Gmb H,Engine Dynamics.[2014-05-25].http://www.mtu.de/company/mtu-worldwide/mtu-aero-engines-polska/.
[3]Schonrock A,Dascotte E,Dufour K H.Validation of an aeroengine carcass finite element model by means of computational model updating based on static stiffness testing[R/OL].BMW Rools-Royce Aero Engines,[2014-05-25].http://www.femtools.com/download.php?id=epf99/.
[4]张大义,母国新,洪杰.航空发动机转子支承系统刚度计算中的几个问题[J].战术导弹技术,2005(2):20-23.ZHANG Dayi,MU Guoxin,HONG Jie.Rigidity calculation methods for rotor supporting system in aeroengine[J].Tactical Missile Technology,2005(2):20-23.(in Chinese)
[5]高金海,洪杰.航空发动机整机动力特性建模技术研究[J].战术导弹技术,2006(2):29-35.GAO Jinhai,HONG Jie.Study of modeling technique for dynamic characteristics of engine casing[J].Tactical Missile Technology,2006(2):29-35.(in Chinese)
[6]陈萌,马燕红,刘书国,等.航空发动机整机有限元模型转子动力学分析[J].北京航空航天大学报,2007,33(9):1013-1016.CHEN Meng,MA Yanhong,LIU Shuguo,et al.Rotordynamic analysis of whole aero-engine models based on finite element method[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(9):1013-1016.(in Chinese)
[7]Zang C,Schwingshackl C W,Ewins D J.Model validation for structural dynamic analysis:an approach to the sandia structural synamics challenge[J].Computer Methods in Applied Mechanics and Engineering,2008(197):2645-2659.
[8]晏砺堂,朱梓根.结构系统动力特性分析[M].北京:北京航空航天大学出版社,1987:25-26.YAN Litang,ZHU Zigen.Dynamics analysis of structures[M].Beijing:Beihang University Press,1987:25-26.(in Chinese)
[9]晏砺堂.航空燃气轮机振动和减振[M].北京:国防工业出版社,1991:30-31.YAN Litang.Vibration characteristics and decreasing method of aeroengine[M].Beijing:National Defense Industry Press,1991:30-31.(in Chinese)
[10]付才高.转子动力学及整机振动[M].北京:航空工业出版社,2000:34.FU Caigao.Rotor dynamics and whole engine vibration[M].Beijing:Aviation Industry Press,2000:34.(in Chinese)
[11]刘长富,邓明.航空发动机结构分析[M].西安:西北工业大学出版社,2006:21.LIU Changfu,DENG Ming.Structural analysis of aeroengine[M].Xi’an:Northwestern Polytechnical University Press,2006:21.(in Chinese)
[12]陈果.航空发动机整机振动耦合动力学模型及其验证[J].航空动力学报,2012,27(2):241-254CHEN Guo.A coupling dynamic model for whole aeroengine vibration and its verification[J].Journal of Aerospace Power,2012,27(2):241-254(in Chinese)
[13]郑旭东,张连祥,刘廷毅.航空发动机整机振动特性及应变能计算与分析[J].航空发动机,2000,26(2):42-46.ZHENG Xudong,ZHANG Lianxiang,LIU Tingyi.Whole engine vibration characteristics and strain energy analysis of aeroengine[J].Aeroengine,2000,26(2):42-46.(in Chinese)
[14]周传月.SAMCEF有限元分析及应用实例[M].北京:机械工业出版社,2009:35.ZHOU Chuanyue.Finite element analysis and application example of SAMCEF[M].Beijing:China Machine Press,2009:35.(in Chinese)
[15]曾攀.有限元分析及应用[M].北京:清华大学出版社,2004:76.ZENG Pan.Finite element analysis and applications[M].Beijing:Tsinghua University Press,2004:76.(in Chinese)